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公开(公告)号：US10119423B2
公开(公告)日：2018-11-06
申请号：US14426252
申请日：2013-09-17
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Charles W. Brown , Christopher M. Quinn , Shelton O. Duelm , Peter V. Tomeo , Corey L. Hubbert
Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.
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公开(公告)号：US20160023429A1
公开(公告)日：2016-01-28
申请号：US14798495
申请日：2015-07-14
Applicant: United Technologies Corporation
Inventor： Sreenivasa R. Voleti , Christopher M. Quinn
CPC classification number: B32B5/12 , B32B5/145 , B32B5/26 , B32B7/12 , B32B27/08 , B32B27/38 , B32B37/14 , B32B2255/10 , B32B2255/20 , B32B2260/023 , B32B2260/046 , B32B2262/02 , B32B2262/0269 , B32B2262/101 , B32B2262/106 , B32B2305/30 , B32B2307/50
Abstract: A composite article includes a laminate structure of at least first and second fiber layers. Each of the layers includes a network of primary reinforcement fibers disposed in a matrix. The layers are bonded to each other along an interface of the matrices. The matrices include a concentration of secondary reinforcement particles locally at the interface to strengthen the interface.
Abstract translation: 复合制品包括至少第一和第二纤维层的层压结构。 每个层包括布置在矩阵中的主增强纤维网。 层沿着矩阵的界面彼此结合。 这些基质在界面处局部地包含二次增强粒子的浓度以加强界面。
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公开(公告)号：US10578120B2
公开(公告)日：2020-03-03
申请号：US15672583
申请日：2017-08-09
Applicant: United Technologies Corporation
Inventor： Shelton O. Duelm , Christopher M. Quinn , Charles W. Brown
Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.
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公开(公告)号：US09909503B2
公开(公告)日：2018-03-06
申请号：US14428379
申请日：2013-02-22
Applicant: United Technologies Corporation
Inventor： Keith T. Salamon , Matthew A. Turner , Christopher M. Quinn
CPC classification number: F02C7/28 , F01D9/02 , F01D11/001 , F02C3/10 , F05D2220/36
Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.
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公开(公告)号：US20150125305A1
公开(公告)日：2015-05-07
申请号：US14171093
申请日：2014-02-03
Applicant: United Technologies Corporation
Inventor： Shelton O. Duelm , Christopher M. Quinn , Charles W. Brown
CPC classification number: F04D29/322 , F01D5/3007 , F01D5/3053 , F01D5/323 , F01D11/008 , F04D29/023 , F04D29/329 , F05D2220/36 , F05D2230/10 , F05D2230/64 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.
Abstract translation: 用于燃气涡轮发动机的风扇的平台包括主体部分，在主体部分的前部的前凸缘，其包括与燃气涡轮发动机的风扇的轮毂的凸耳的前凸缘相互作用的接合特征 以及与主体部分的后部一体形成的销。 引脚可接收在凸耳的后凸缘中的孔中。
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Patent Agency Ranking
公开(公告)号：US10724397B2
公开(公告)日：2020-07-28
申请号：US15836254
申请日：2017-12-08
Applicant: United Technologies Corporation
Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.
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公开(公告)号：US10046539B2
公开(公告)日：2018-08-14
申请号：US14798495
申请日：2015-07-14
Applicant: United Technologies Corporation
Inventor： Sreenivasa R. Voleti , Christopher M. Quinn
Abstract: A composite article includes a laminate structure of at least first and second fiber layers. Each of the layers includes a network of primary reinforcement fibers disposed in a matrix. The layers are bonded to each other along an interface of the matrices. The matrices include a concentration of secondary reinforcement particles locally at the interface to strengthen the interface.
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公开(公告)号：US20170335859A1
公开(公告)日：2017-11-23
申请号：US15672583
申请日：2017-08-09
Applicant: United Technologies Corporation
Inventor： Shelton O. Duelm , Christopher M. Quinn , Charles W. Brown
Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.
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公开(公告)号：US09759226B2
公开(公告)日：2017-09-12
申请号：US14171093
申请日：2014-02-03
Applicant: United Technologies Corporation
Inventor： Shelton O. Duelm , Christopher M. Quinn , Charles W. Brown
CPC classification number: F04D29/322 , F01D5/3007 , F01D5/3053 , F01D5/323 , F01D11/008 , F04D29/023 , F04D29/329 , F05D2220/36 , F05D2230/10 , F05D2230/64 , F05D2300/43 , F05D2300/603 , Y02T50/672
Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.
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公开(公告)号：US20160130952A1
公开(公告)日：2016-05-12
申请号：US14903076
申请日：2014-06-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sreenivasa R. Voleti , Christopher M. Quinn
CPC classification number: F01D5/26 , F01D5/16 , F01D5/282 , F01D9/041 , F04D29/023 , F04D29/324 , F05D2220/32 , F05D2230/30 , F05D2240/12 , F05D2240/30 , F05D2300/224 , F05D2300/603 , F05D2300/614
Abstract: A turbine engine component (100) comprises a fiber structure (125, 126) forming at least a portion of an airfoil (102). A matrix (128) embeds the fiber structure. A carbon nanotube filler (130) is in the matrix.
Abstract translation: 涡轮发动机部件（100）包括形成翼型件（102）的至少一部分的纤维结构（125,126）。 矩阵（128）嵌入光纤结构。 碳纳米管填料（130）在基质中。
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